CA1037870A - Bucket locking mechanism - Google Patents
Bucket locking mechanismInfo
- Publication number
- CA1037870A CA1037870A CA240,210A CA240210A CA1037870A CA 1037870 A CA1037870 A CA 1037870A CA 240210 A CA240210 A CA 240210A CA 1037870 A CA1037870 A CA 1037870A
- Authority
- CA
- Canada
- Prior art keywords
- slot
- disc
- block
- blade
- platform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/326—Locking of axial insertion type blades by other means
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Fire-Extinguishing Compositions (AREA)
Abstract
BUCKET LOCKING MECHANISM
Abstract of the Disclosure An arrangement for axially locking a turbomachinery blade in its associated disc slot includes a locking key, a keyway formed in the blade platform and a circumferential slot formed in the periphery of the disc. The locking key is recessed in the platform keyway to permit insertion of the blade and is then dropped into the disc slot and rotated 90° to lock the blade to the disc.
Abstract of the Disclosure An arrangement for axially locking a turbomachinery blade in its associated disc slot includes a locking key, a keyway formed in the blade platform and a circumferential slot formed in the periphery of the disc. The locking key is recessed in the platform keyway to permit insertion of the blade and is then dropped into the disc slot and rotated 90° to lock the blade to the disc.
Description
10378qO
BUCKET LOCKING MECHANISM
This invention relates to turbomachines and, more particularly, to improved means for axially retaining a blade or bucket in a tur-bomachinery rotor or disc.
Background of the Invention Blade locks which have been heretofore proposed for use in axially locking a blade within a generally axially extending rotor or disc slot have usually included a member which extends axially across the disc adjacent the blade or bucket root. A great number of these locking devices have included one or more tabs that are ~ -bent after assembly to axially lock the rotor in its slot. Such arrangements are, however, undesirable in that the axial forces required to retain the blade in its slot are usually reacted by a member which has been bent during assembly. In addition, the bent tab usually has some residual strain which may result in spring-back of the bent tab and axial looseness of the blade.
Another solution has employed the use of both a spacer and alocking clip so that the tab that is bent at assembly retains only the spacer. While this solution overcomes the problem of r~acting axial blade forces through a tab that is bent at assembly and the problem of tab spring-back, it does require two parts, access to at least one side of the turbomachinery disc, and the bending at assembly of one tab to retain the spacer.
A further solution to axially locking a turbine blade is shown in U.S. patent 2,867,408, issued January 6, 1959, and involves a i 25 locking key that is engaged in a rotor slot and a platform slot.
To lock the array of blades in place using the arrangement shown in the aforementioned patent, however, the last key must be expanded by peening so as to fill the slots formed in adjacent blade plat-forms. Moreover, with such an arrangement, to remove and replace one blade, all blades would have to be removed.
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, . , r 1037~70 .: `- .
:
A primary object of this invention, then is to provide a blade retainer or lock that does not require the bending of any tabs at assembly; that permits the blade to be locked to the disc without access to either side of the disc; and that enables removal and replacement of a single blade.
Summary of the Invention Briefly stated, the present invention provides a locking key which includes a rectangular block portion with a generally cylin-drical stem extending therefrom. A keyway is formed in the plat- -form portion of the turbomachinery blade to receive the locking key from the underside of the platform, with the block portion recessed into a slot and the stem projecting through an opening formed in the platform. A keyway slot is formed in outer circumferential surface of the disc in a position under the platform keyway. The block portion of the key has a length dimension greater than its width dimension. The axial length of the platform slot is sized to ~ ;
correspond to the smaller width dimension of the locking key block, .~ . . . .
- whereas the axial length of the disc keyway slot is sized to correspond to the longer length dimension of the locking key block. In this -manner, the locking key may be dropped radially into the disc key-way slot and rotated 90 to axially lock the blade to the disc.
Suitable means such as a screw driver slot may be provided at the distal end of the locking key stem to facilitate rotating the locking key into and out of its locked position.
The stem may be conveniently staked or otherwise suitable secured to the platform t~ prevent the locking key from rotating out of its locked position during operation of the bladed turbo-machinery disc. -Brief Description of the Drawings While the specification concludes with claims particularly poin-ting out and distinctly claiming the subject m~`tter of this invention~
'",~
'~, ', . .
,,:' .
~037870 .. . .
it is believed that the invention will be better understood upon reading the following description of the preferred embodiment in conjunction with the accompanying drawings, wherein~
'' .
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~,037Bqo FIGURE 1 is a partial perspective view showing an exemplary bladed turbomachinery disc employi.ng the blade locking means of this invention;
FIGURE 2 is an enlarged perspective view showing the locking :. 5 key of this invention;
FIGURE 3 is an enlarged partial cross-sectional view taken along lines 3-3 of FIGURE l;
FIGURE 4 is a view like that of FIGURE 3 showing the locking .; key of FIGURE 2 in its position enabling insertion of the blade 10 into its associated disc slot; ; . -... ..
.*
FIGURE 5 is an enlarged fragmentary plan view taken along lines 5-5 of FIGURE 3 and showing the locking key of FIGURE 2 in its : locked position;
: FIGURE 6 is a view like FIGURE 5 taken on lines 6-6 of FIGURE
: 15 4 and showing the locking key of FIGURE 2 in its unlocked position;
FIGURE 7 is a partial perspective view like that of FIGURE 1, but with the blade removed from its disc slot;
FIGURE 8 is an enlarged fragmentary cross-sectional view taken .
; along lines 8-8 of FIGURE 4 and showing the locking key of FIGURE
20 2 in its unlocked position; and .
. FIGURE 9 is a view taken on lines 9-9 of FIGURE 3 showing the locking key of FIGURE 2 in its locked position.
Detailed Description of the Invention . ;
With reference now to the drawings and particularly to Figure 1, ~, 25 a bladed turbomachinery rotor or disc has been shown generally at ~; 10 as comprising a rotata~le annular disc 12 supporting at its per-iphery a plurality of radially extending blades or buckets 14. The blades 14 include an airfoil portion 16, a platform portion 18 and .~
a root portion 20. The disc 12 is formed with a slot 22 for each ~ -30 blade 14 which extends generally axially across the disc 12 at its .:
periphery and is shaped, in cooperation with the blade root 22, to axially receive the blade root and to radially lock the blade 14 to the disc against centrifugal forces.
, ' ' ' . ` . ' ' ~ ' 1~, ~ . ' 1()37~70 As shown in Figure 1, the blade platforms 18 extend over the - outer circumferential surface 23 of the disc 12 so as to form the inner boundary of fluid flow across the blade airfoils 16.
The means of this invention for axially locking the blade root 20 in the disc slot 22 include a locking key 24 and associated key-ways 26 and 28 formed, respectively, in the blade platform and the outer peripherial surface 23 of the disc 12.
With reference now to Figure 2 the locking key 24 has been shown ., as including a block portion 30 and a stem portion 32. The block portion 30 is generally rectangular in shape and has a radial thickness "t", a width "w", and a ~e~gth "1". The stem portion 32 is preferably cylindrical and extends normally from the central portion of the radially outwardly facing surface of the block 30.
The outer radial end 34 of the stem 32 is formed with a screw driver slot or other suitable means 35 to enable rotation of the key 24 into its locked position as will be hereinafter described.
With reference now to Figures 3, 4 and 5, the platform keyway 26 includes a slot 36 formed in the radially inner side of the platform 18 and an opening 38 communicating with the slot 36 and extending radially through the blade platform 18. As best shown in Figure 5 .
the axial width "W" of the platf~`rm slot 36 is sized to receive the width dimension "w" of the locking key block 30 and has a radial height sized to receive the thickness dimension "t" of the ke~
block 30 in noninterfering relationship with the disc periphery 23, with the stem portion 32 extending through the keyway opening 38 as ~ -shown in Figure 4.
The disc keyway 28 takes the form of a circumferential slot which has an axial length "L" and radial height "T", as shown in figure 3, which are sized, respectively, to correspond to the length dimension "1" and the thickness dimension "t" of the block 30.
The slot 28 is located axially so that when the blade 14 and root portion 20 are inserted in the disc slot 22, the slot 28 will be aligned with the keyway 26 formed in the blade platform 18.
:
~ 0378~70 .
The use, operation and function of the present invention are as follows. The locking key 24 is inserted into the platform k~y-way 26 as shown in Figures 4 and 6, with the block portion received within platform slot 36 and the stem portion 32 projecting through : 5 platform opening 38. The blade 14 is then axially inserted into its respective rotor slot 22.
; With the blade positioned within its rotor slot 22 as shown in Figure 4, the locking key 24 is dropped radially inward so that the block portion 30 engages the disc keyway 28. The locking key 10 24 is then rotated 90, using slot means 35, from the unlocked position of Figures 6 and 8 to the locked position of Figures 5 and 9, wherein the length dimension "1" of the block 30 is oriented in an axial direction.
Opposed corners of the block 30 are appropriately contoured, as -, 15 at 40 in Figures 2, 6 and 8, so as to permit the key 24 to be rotated or cammed 90 into locking engagement with the slot 28.
Since the axial length or "W" dimension of the platform slot is smaller than the axial length or "L" dimension of the rotor slot, -~
the locking key is radially retained in its locked position of ~-Figures 3, 5 and 9 by abutment of the radially outer face of block 30 with the radially inner side of the blade platform 18. At the same time, axial movement of the blade is prevented by abutment of the locking key stem 32 with the walls of platform opening 38 and by abutment of the block 30 with the disc slot 28.
As best shown in Figures 1 and 3, the stem 32 is preferably sized, for aerodynamic reasons, so that when the locking key 24 is engaged `
in its locked position in the disc slot 28, the distal or outer radial end 34 will be generally flush with the outer surface of the platform.
During operation of the turbomachine, to prevent the locking key from rotating from its locked position of Figures 5 and 9 to its -unlocked position of Figures 6 and 8, the distal end of the stem 32 may be staked to the platform 18 as shown in Figure 5 or otherwise suitabley secured. In this regard, suitable slots :
BUCKET LOCKING MECHANISM
This invention relates to turbomachines and, more particularly, to improved means for axially retaining a blade or bucket in a tur-bomachinery rotor or disc.
Background of the Invention Blade locks which have been heretofore proposed for use in axially locking a blade within a generally axially extending rotor or disc slot have usually included a member which extends axially across the disc adjacent the blade or bucket root. A great number of these locking devices have included one or more tabs that are ~ -bent after assembly to axially lock the rotor in its slot. Such arrangements are, however, undesirable in that the axial forces required to retain the blade in its slot are usually reacted by a member which has been bent during assembly. In addition, the bent tab usually has some residual strain which may result in spring-back of the bent tab and axial looseness of the blade.
Another solution has employed the use of both a spacer and alocking clip so that the tab that is bent at assembly retains only the spacer. While this solution overcomes the problem of r~acting axial blade forces through a tab that is bent at assembly and the problem of tab spring-back, it does require two parts, access to at least one side of the turbomachinery disc, and the bending at assembly of one tab to retain the spacer.
A further solution to axially locking a turbine blade is shown in U.S. patent 2,867,408, issued January 6, 1959, and involves a i 25 locking key that is engaged in a rotor slot and a platform slot.
To lock the array of blades in place using the arrangement shown in the aforementioned patent, however, the last key must be expanded by peening so as to fill the slots formed in adjacent blade plat-forms. Moreover, with such an arrangement, to remove and replace one blade, all blades would have to be removed.
'~"d~ :---1-- q~ , ~, . . .
, . , r 1037~70 .: `- .
:
A primary object of this invention, then is to provide a blade retainer or lock that does not require the bending of any tabs at assembly; that permits the blade to be locked to the disc without access to either side of the disc; and that enables removal and replacement of a single blade.
Summary of the Invention Briefly stated, the present invention provides a locking key which includes a rectangular block portion with a generally cylin-drical stem extending therefrom. A keyway is formed in the plat- -form portion of the turbomachinery blade to receive the locking key from the underside of the platform, with the block portion recessed into a slot and the stem projecting through an opening formed in the platform. A keyway slot is formed in outer circumferential surface of the disc in a position under the platform keyway. The block portion of the key has a length dimension greater than its width dimension. The axial length of the platform slot is sized to ~ ;
correspond to the smaller width dimension of the locking key block, .~ . . . .
- whereas the axial length of the disc keyway slot is sized to correspond to the longer length dimension of the locking key block. In this -manner, the locking key may be dropped radially into the disc key-way slot and rotated 90 to axially lock the blade to the disc.
Suitable means such as a screw driver slot may be provided at the distal end of the locking key stem to facilitate rotating the locking key into and out of its locked position.
The stem may be conveniently staked or otherwise suitable secured to the platform t~ prevent the locking key from rotating out of its locked position during operation of the bladed turbo-machinery disc. -Brief Description of the Drawings While the specification concludes with claims particularly poin-ting out and distinctly claiming the subject m~`tter of this invention~
'",~
'~, ', . .
,,:' .
~037870 .. . .
it is believed that the invention will be better understood upon reading the following description of the preferred embodiment in conjunction with the accompanying drawings, wherein~
'' .
' .
-2a-' .-. , :::.. . :., . , . .. , . ... :~ . :,~
~,037Bqo FIGURE 1 is a partial perspective view showing an exemplary bladed turbomachinery disc employi.ng the blade locking means of this invention;
FIGURE 2 is an enlarged perspective view showing the locking :. 5 key of this invention;
FIGURE 3 is an enlarged partial cross-sectional view taken along lines 3-3 of FIGURE l;
FIGURE 4 is a view like that of FIGURE 3 showing the locking .; key of FIGURE 2 in its position enabling insertion of the blade 10 into its associated disc slot; ; . -... ..
.*
FIGURE 5 is an enlarged fragmentary plan view taken along lines 5-5 of FIGURE 3 and showing the locking key of FIGURE 2 in its : locked position;
: FIGURE 6 is a view like FIGURE 5 taken on lines 6-6 of FIGURE
: 15 4 and showing the locking key of FIGURE 2 in its unlocked position;
FIGURE 7 is a partial perspective view like that of FIGURE 1, but with the blade removed from its disc slot;
FIGURE 8 is an enlarged fragmentary cross-sectional view taken .
; along lines 8-8 of FIGURE 4 and showing the locking key of FIGURE
20 2 in its unlocked position; and .
. FIGURE 9 is a view taken on lines 9-9 of FIGURE 3 showing the locking key of FIGURE 2 in its locked position.
Detailed Description of the Invention . ;
With reference now to the drawings and particularly to Figure 1, ~, 25 a bladed turbomachinery rotor or disc has been shown generally at ~; 10 as comprising a rotata~le annular disc 12 supporting at its per-iphery a plurality of radially extending blades or buckets 14. The blades 14 include an airfoil portion 16, a platform portion 18 and .~
a root portion 20. The disc 12 is formed with a slot 22 for each ~ -30 blade 14 which extends generally axially across the disc 12 at its .:
periphery and is shaped, in cooperation with the blade root 22, to axially receive the blade root and to radially lock the blade 14 to the disc against centrifugal forces.
, ' ' ' . ` . ' ' ~ ' 1~, ~ . ' 1()37~70 As shown in Figure 1, the blade platforms 18 extend over the - outer circumferential surface 23 of the disc 12 so as to form the inner boundary of fluid flow across the blade airfoils 16.
The means of this invention for axially locking the blade root 20 in the disc slot 22 include a locking key 24 and associated key-ways 26 and 28 formed, respectively, in the blade platform and the outer peripherial surface 23 of the disc 12.
With reference now to Figure 2 the locking key 24 has been shown ., as including a block portion 30 and a stem portion 32. The block portion 30 is generally rectangular in shape and has a radial thickness "t", a width "w", and a ~e~gth "1". The stem portion 32 is preferably cylindrical and extends normally from the central portion of the radially outwardly facing surface of the block 30.
The outer radial end 34 of the stem 32 is formed with a screw driver slot or other suitable means 35 to enable rotation of the key 24 into its locked position as will be hereinafter described.
With reference now to Figures 3, 4 and 5, the platform keyway 26 includes a slot 36 formed in the radially inner side of the platform 18 and an opening 38 communicating with the slot 36 and extending radially through the blade platform 18. As best shown in Figure 5 .
the axial width "W" of the platf~`rm slot 36 is sized to receive the width dimension "w" of the locking key block 30 and has a radial height sized to receive the thickness dimension "t" of the ke~
block 30 in noninterfering relationship with the disc periphery 23, with the stem portion 32 extending through the keyway opening 38 as ~ -shown in Figure 4.
The disc keyway 28 takes the form of a circumferential slot which has an axial length "L" and radial height "T", as shown in figure 3, which are sized, respectively, to correspond to the length dimension "1" and the thickness dimension "t" of the block 30.
The slot 28 is located axially so that when the blade 14 and root portion 20 are inserted in the disc slot 22, the slot 28 will be aligned with the keyway 26 formed in the blade platform 18.
:
~ 0378~70 .
The use, operation and function of the present invention are as follows. The locking key 24 is inserted into the platform k~y-way 26 as shown in Figures 4 and 6, with the block portion received within platform slot 36 and the stem portion 32 projecting through : 5 platform opening 38. The blade 14 is then axially inserted into its respective rotor slot 22.
; With the blade positioned within its rotor slot 22 as shown in Figure 4, the locking key 24 is dropped radially inward so that the block portion 30 engages the disc keyway 28. The locking key 10 24 is then rotated 90, using slot means 35, from the unlocked position of Figures 6 and 8 to the locked position of Figures 5 and 9, wherein the length dimension "1" of the block 30 is oriented in an axial direction.
Opposed corners of the block 30 are appropriately contoured, as -, 15 at 40 in Figures 2, 6 and 8, so as to permit the key 24 to be rotated or cammed 90 into locking engagement with the slot 28.
Since the axial length or "W" dimension of the platform slot is smaller than the axial length or "L" dimension of the rotor slot, -~
the locking key is radially retained in its locked position of ~-Figures 3, 5 and 9 by abutment of the radially outer face of block 30 with the radially inner side of the blade platform 18. At the same time, axial movement of the blade is prevented by abutment of the locking key stem 32 with the walls of platform opening 38 and by abutment of the block 30 with the disc slot 28.
As best shown in Figures 1 and 3, the stem 32 is preferably sized, for aerodynamic reasons, so that when the locking key 24 is engaged `
in its locked position in the disc slot 28, the distal or outer radial end 34 will be generally flush with the outer surface of the platform.
During operation of the turbomachine, to prevent the locking key from rotating from its locked position of Figures 5 and 9 to its -unlocked position of Figures 6 and 8, the distal end of the stem 32 may be staked to the platform 18 as shown in Figure 5 or otherwise suitabley secured. In this regard, suitable slots :
Claims (5)
1. In a turbomachine of the type including a rotatable disc formed with at least one slot extending generally axially of said disc at its periphery, a blade extending generally radially from said disc and having a root portion engaged in said axial slot and a platform portion, extending over a portion of the periphery of said disc, said axial slot and said root portion sized and formed to abut and radially lock the blade to the disc against centrifugal forces, means for axially retaining said blade root in said axial slot comprising:
a locking key having a block portion and an elongated stem portion extending therefrom and terminating at a distal end;
said block portion having a thickness defined by radially in-wardly and outwardly facing surfaces, a width, and a length of greater extent than said width, said stem extending normally from a central portion of said radially outwardly facing block surface;
said platofrm portion formed with a circumferentially extending slot in its radially inner side, said platform slot having an axial width sized to receive the width dimension of said block in close fitting relationship thereto and having a radial height sized to receive said block in noninterfering relation with said disc, a radial opening farmed through said platform portion and communicating with said platform slot for receiving said stem portion, in close fitting relationship therewith, when said block is engaged in said platform groove and for providing access to the distal end of said stem;
a circumferential slot formed in the periphery of said disc adjacent said axial slot, said disc circumferential slot having an axial length sized to receive the length dimension of said block in close fitting relationship therewith, said disc circumferential slot located and having a radial depth such that when said blade is inserted into said axial disc slot, said locking block may be dropped radially out of engagement with said platform slot and into engagement with said disc peripherial slot and then rotated to axially lock the blade in the axial disc slot.
a locking key having a block portion and an elongated stem portion extending therefrom and terminating at a distal end;
said block portion having a thickness defined by radially in-wardly and outwardly facing surfaces, a width, and a length of greater extent than said width, said stem extending normally from a central portion of said radially outwardly facing block surface;
said platofrm portion formed with a circumferentially extending slot in its radially inner side, said platform slot having an axial width sized to receive the width dimension of said block in close fitting relationship thereto and having a radial height sized to receive said block in noninterfering relation with said disc, a radial opening farmed through said platform portion and communicating with said platform slot for receiving said stem portion, in close fitting relationship therewith, when said block is engaged in said platform groove and for providing access to the distal end of said stem;
a circumferential slot formed in the periphery of said disc adjacent said axial slot, said disc circumferential slot having an axial length sized to receive the length dimension of said block in close fitting relationship therewith, said disc circumferential slot located and having a radial depth such that when said blade is inserted into said axial disc slot, said locking block may be dropped radially out of engagement with said platform slot and into engagement with said disc peripherial slot and then rotated to axially lock the blade in the axial disc slot.
2. The combination of claim 1 further characterized in that the distal end of said stem portion includes means to facilitate rotation of said locking key into and out of its locking position.
3. The combination of claim 1 further characterized in that said stem portion is cylindrical.
4. The combination of claim 1 further characterized in that said block is generally rectangular and includes diametrically opposed arcuate surfaces to permit rotation into its locking position.
5. The combination of claim 1 further characterized in that said stem portion is staked to said platform portion to prevent said block from rotating out of its locked position.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US527586A US3904317A (en) | 1974-11-27 | 1974-11-27 | Bucket locking mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1037870A true CA1037870A (en) | 1978-09-05 |
Family
ID=24102083
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA240,210A Expired CA1037870A (en) | 1974-11-27 | 1975-11-20 | Bucket locking mechanism |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US3904317A (en) |
| JP (1) | JPS5848729B2 (en) |
| CA (1) | CA1037870A (en) |
| DE (1) | DE2516061C2 (en) |
| FR (1) | FR2292856A1 (en) |
| GB (1) | GB1499379A (en) |
| IT (1) | IT1037743B (en) |
| NL (1) | NL7504670A (en) |
| NO (1) | NO147427C (en) |
Families Citing this family (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH581783A5 (en) * | 1975-01-30 | 1976-11-15 | Bbc Sulzer Turbomaschinen | |
| US4135857A (en) * | 1977-06-09 | 1979-01-23 | United Technologies Corporation | Reduced drag airfoil platforms |
| JPS5482505A (en) * | 1977-12-14 | 1979-06-30 | Hitachi Ltd | Steam turbine |
| US4400137A (en) * | 1980-12-29 | 1983-08-23 | Elliott Turbomachinery Co., Inc. | Rotor assembly and methods for securing a rotor blade therewithin and removing a rotor blade therefrom |
| US4451959A (en) * | 1980-12-29 | 1984-06-05 | Elliott Turbomachinery Company, Inc. | Methods for securing a rotor blade within a rotor assembly and removing a rotor blade therefrom |
| US4676723A (en) * | 1986-03-26 | 1987-06-30 | Westinghouse Electric Corp. | Locking system for a turbine side entry blade |
| US4820126A (en) * | 1988-02-22 | 1989-04-11 | Westinghouse Electric Corp. | Turbomachine rotor assembly having reduced stress concentrations |
| US4915587A (en) * | 1988-10-24 | 1990-04-10 | Westinghouse Electric Corp. | Apparatus for locking side entry blades into a rotor |
| US5242270A (en) * | 1992-01-31 | 1993-09-07 | Westinghouse Electric Corp. | Platform motion restraints for freestanding turbine blades |
| GB9412963D0 (en) * | 1994-06-28 | 1994-09-28 | Rolls Royce Plc | Gas turbine engine fan blade assembly |
| GB2299834B (en) * | 1995-04-12 | 1999-09-08 | Rolls Royce Plc | Gas turbine engine rotary disc |
| US5720596A (en) * | 1997-01-03 | 1998-02-24 | Westinghouse Electric Corporation | Apparatus and method for locking blades into a rotor |
| US20040115059A1 (en) * | 2002-12-12 | 2004-06-17 | Kehl Richard Eugene | Cored steam turbine bucket |
| GB2397854A (en) * | 2003-01-30 | 2004-08-04 | Rolls Royce Plc | Securing blades in a rotor assembly |
| GB2406144A (en) * | 2003-09-19 | 2005-03-23 | Rolls Royce Plc | Gas turbine engine blade retention system using a key |
| DE102004054930A1 (en) * | 2004-11-13 | 2006-05-18 | Mtu Aero Engines Gmbh | Rotor of a turbomachine, in particular gas turbine rotor |
| JP4886735B2 (en) * | 2008-05-26 | 2012-02-29 | 株式会社東芝 | Turbine blade assembly and steam turbine |
| JP5149831B2 (en) * | 2009-02-12 | 2013-02-20 | 三菱重工コンプレッサ株式会社 | Turbine blade fixed structure and turbine |
| US8714929B2 (en) * | 2010-11-10 | 2014-05-06 | General Electric Company | Turbine assembly and method for securing a closure bucket |
| US20130052024A1 (en) * | 2011-08-24 | 2013-02-28 | General Electric Company | Turbine Nozzle Vane Retention System |
| US9051845B2 (en) * | 2012-01-05 | 2015-06-09 | General Electric Company | System for axial retention of rotating segments of a turbine |
| CN106015086B (en) * | 2016-06-02 | 2018-11-09 | 东方电气集团东方汽轮机有限公司 | A kind of axial lock structure of compressor blade in the impeller wheel groove |
| FR3056630B1 (en) * | 2016-09-26 | 2018-12-07 | Safran Aircraft Engines | FLOW MONOBLOC BLOWER DISK FOR AIRCRAFT TURBOMACHINE |
| CN113623270B (en) * | 2021-08-24 | 2024-04-16 | 中国联合重型燃气轮机技术有限公司 | Locking device and gas compressor and gas turbine comprising same |
| JP2023090250A (en) * | 2021-12-17 | 2023-06-29 | 三菱重工コンプレッサ株式会社 | Rotor of steam turbine, steam turbine, and fixing method of rotor blade |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB725461A (en) * | 1953-04-10 | 1955-03-02 | Parsons C A & Co Ltd | Improvements in and relating to the axial locking of rotor blades for turbines and the like |
| US2949278A (en) * | 1956-07-05 | 1960-08-16 | Gen Motors Corp | Turbine blade retention |
| US3198485A (en) * | 1963-09-26 | 1965-08-03 | Gen Motors Corp | Turbine blade lock |
-
1974
- 1974-11-27 US US527586A patent/US3904317A/en not_active Expired - Lifetime
-
1975
- 1975-04-12 DE DE2516061A patent/DE2516061C2/en not_active Expired
- 1975-04-16 NO NO751348A patent/NO147427C/en unknown
- 1975-04-18 NL NL7504670A patent/NL7504670A/en not_active Application Discontinuation
- 1975-04-21 JP JP50047599A patent/JPS5848729B2/en not_active Expired
- 1975-04-23 GB GB16783/75A patent/GB1499379A/en not_active Expired
- 1975-04-30 IT IT22872/75A patent/IT1037743B/en active
- 1975-11-20 CA CA240,210A patent/CA1037870A/en not_active Expired
- 1975-11-27 FR FR7536281A patent/FR2292856A1/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| DE2516061C2 (en) | 1983-07-28 |
| NO751348L (en) | 1976-05-31 |
| NL7504670A (en) | 1976-05-31 |
| NO147427B (en) | 1982-12-27 |
| JPS5162204A (en) | 1976-05-29 |
| FR2292856A1 (en) | 1976-06-25 |
| JPS5848729B2 (en) | 1983-10-31 |
| IT1037743B (en) | 1979-11-20 |
| US3904317A (en) | 1975-09-09 |
| DE2516061A1 (en) | 1976-08-12 |
| GB1499379A (en) | 1978-02-01 |
| NO147427C (en) | 1983-04-06 |
| FR2292856B1 (en) | 1980-01-25 |
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